CN114718657A - Local high-efficient cooling structure of turbine blade back of blade - Google Patents
Local high-efficient cooling structure of turbine blade back of blade Download PDFInfo
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- CN114718657A CN114718657A CN202210369115.2A CN202210369115A CN114718657A CN 114718657 A CN114718657 A CN 114718657A CN 202210369115 A CN202210369115 A CN 202210369115A CN 114718657 A CN114718657 A CN 114718657A
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- 238000001816 cooling Methods 0.000 title claims abstract description 90
- 239000000112 cooling gas Substances 0.000 abstract description 12
- 230000000694 effects Effects 0.000 abstract description 8
- 239000007789 gas Substances 0.000 description 5
- 238000010521 absorption reaction Methods 0.000 description 3
- 238000004378 air conditioning Methods 0.000 description 3
- 230000003068 static effect Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The application belongs to the field of cooling design of turbine blades, and relates to a local efficient cooling device for a turbine blade back, which comprises an inner layer wall, a middle layer wall and an outer layer wall; the inner layer wall is provided with a first impact hole, the middle layer wall is provided with a second impact hole, the outer layer wall is provided with an air film hole, a first cooling cavity is formed between the inner layer wall and the middle layer wall, and a second cooling cavity is formed between the middle layer wall and the outer layer wall; when the turbine blade is cooled, cooling gas enters the blade, then directly enters the first impact hole and flows out, and is subjected to impact cooling in the first cooling cavity; the heat exchange area of the cold air side is greatly increased, the wall temperature level of the blade is greatly reduced under the comprehensive action, and the cooling effect of the blade is improved.
Description
Technical Field
The utility model belongs to turbine blade cooling design field, in particular to local high-efficient cooling structure of turbine blade back.
Background
As shown in fig. 1 and 2, the virtual frame area of the blade back position of the high-pressure turbine blade is usually one of the highest heat exchange load positions, and in order to ensure that the position works reliably for a long time in the allowable temperature range of the material, the position needs to be cooled efficiently, a composite cooling mode of 'impact + convection + air film' is usually adopted during cooling, and a typical cooling structure form is a built-in impact conduit and double-wall structure form.
With the increase of thrust-weight ratio of military engines, the inlet temperature of the turbine is about 2200K or more, the design of the cooling structure of the turbine blade is required to be higher, and the current conventional cooling structure cannot meet the requirement of cooling in the future.
Therefore, in order to solve the heat exchange problem at the local position of the blade back, a new and efficient cooling structure form is needed.
Disclosure of Invention
The utility model provides a local high-efficient cooling structure of turbine blade back to adopt among the solution prior art to strike pipe and the problem that the double-walled structure form is difficult to satisfy current cooling demand.
The technical scheme of the application is as follows: a local high-efficiency cooling structure for a turbine blade back comprises an inner layer wall, a middle layer wall and an outer layer wall; the inner layer wall is provided with a first impact hole, the middle layer wall is provided with a second impact hole, the outer layer wall is provided with an air film hole, a first cooling cavity is formed between the inner layer wall and the middle layer wall, and a second cooling cavity is formed between the middle layer wall and the outer layer wall; the first impact hole and the second impact hole are positioned at different positions in the radial direction of the blade, and the second impact hole and the air film hole are positioned at different positions in the radial direction of the blade; a first flow disturbing column is connected between the inner layer wall and the middle layer wall, and a second flow disturbing column is connected between the middle layer wall and the outer layer wall; the first turbulence column and the first impact hole as well as the second turbulence column and the second impact hole are respectively positioned at different radial positions of the blade.
Preferably, the first cooling chamber includes a first impingement area, a first turbulence area and a first convection area, the first impingement area is disposed corresponding to the first impingement hole, the first turbulence area is disposed around the first turbulence column, and the first convection area is disposed corresponding to the second impingement hole.
Preferably, the second cooling chamber includes a second impingement area, a second turbulence area and a second convection area, the second impingement area is disposed corresponding to the second impingement hole, the second turbulence area is disposed around the second turbulence column, and the second convection area is disposed corresponding to the film hole; the first impact holes and the second impact areas are arranged in a staggered mode, and the first convection areas and the second convection areas are arranged in a staggered mode.
Preferably, the first and second turbulence columns are radially staggered.
Preferably, the first impact hole is arranged corresponding to the air film hole.
The local high-efficiency cooling device for the blade back of the turbine blade comprises an inner layer wall, a middle layer wall and an outer layer wall; the inner layer wall is provided with a first impact hole, the middle layer wall is provided with a second impact hole, the outer layer wall is provided with an air film hole, a first cooling cavity is formed between the inner layer wall and the middle layer wall, and a second cooling cavity is formed between the middle layer wall and the outer layer wall; when the turbine blade is cooled, cooling air directly enters the first impact hole and flows out after entering the blade, and is subjected to impact cooling in the first cooling chamber; because the cooling gas just can follow the gas film hole and flow after first cooling chamber and second cooling chamber, the heat transfer area of cold gas side increases by a wide margin, makes air conditioning more fully absorb heat along the journey, through twice impact heat transfer simultaneously, has reduced the wall temperature level of blade by a wide margin under the combined action, has improved the cooling effect of blade.
Drawings
In order to more clearly illustrate the technical solutions provided by the present application, the following briefly introduces the accompanying drawings. It is to be expressly understood that the drawings described below are only illustrative of some embodiments of the invention.
FIG. 1 is a schematic diagram of a cooling structure of an impingement duct of the prior art;
FIG. 2 is a schematic view of a double-walled cooling structure in the prior art;
FIG. 3 is a partial axial schematic view of a blade back cooling structure according to the present application;
FIG. 4 is a schematic cross-sectional view of a cooling structure of the blade back of the present application.
1. An inner wall; 2. a first impingement hole; 3. a middle-layer wall; 4. a second impingement hole; 5. a first cooling chamber; 6. a second cooling chamber; 7. a gas film hole; 8. a first turbulence column; 9. a second turbulence column; 10. a first impact zone; 11. a first turbulent flow region; 12. a first convection zone; 13. a second impact zone; 14. a second turbulence area; 15. a second convection zone; 16. an outer wall.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
A local high-efficiency cooling device for a blade back of a turbine blade is characterized in that a three-layer wall structure is adopted for cooling the blade back, the blade back structure is obtained by analyzing the blade back structure, the thickness of a blade profile at the position of the blade back is the largest, enough design space can be provided for the cooling structure with the three layers of walls, and the device has realizability in spatial layout; in addition, from the static pressure distribution of the blade profile, the static pressure at the position is low, the sufficient cold air outflow margin is provided, powerful conditions are provided for cold air flowing and heat exchange in the three-layer wall cooling structure, and therefore the three-layer wall efficient cooling structure has realizability in space and function.
As shown in fig. 3 and 4, comprises an inner wall 1, a middle wall 3 and an outer wall 16. The inner layer wall 1 is provided with a first impact hole 2, the middle layer wall 3 is provided with a second impact hole 4, the outer layer wall 16 is provided with a gas film hole 7, a first cooling chamber 5 is formed between the inner layer wall 1 and the middle layer wall 3, and a second cooling chamber 6 is formed between the middle layer wall 3 and the outer layer wall 16; the first impact hole 2 and the second impact hole 4 are positioned at different positions in the radial direction of the blade, and the second impact hole 4 and the air film hole 7 are positioned at different positions in the radial direction of the blade; a first flow disturbing column 8 is connected between the inner layer wall 1 and the middle layer wall 3, and a second flow disturbing column 9 is connected between the middle layer wall 3 and the outer layer wall 16; the first turbulence column 8 and the first impact hole 2, and the second turbulence column 9 and the second impact hole are respectively arranged at different positions in the radial direction of the blade.
The first impingement holes 2 are uniformly arranged in the inner wall 1, the second impingement holes 4 are uniformly arranged in the middle wall 3, and the air film holes 7 are uniformly arranged in the outer wall 16.
When cooling turbine blade, the cooling gas enters into inside the blade after, directly enters into in the first impact hole 2 and flows out, to carrying out impingement cooling in the first cooling cavity 5, and back cooling gas flows along first cooling cavity 5, carry out the vortex to the cooling gas behind first vortex post 8, make the flow even, carry out strong wave convection heat transfer to the wall simultaneously, then enter into the second and strike in the hole 4 and flow out, to carrying out impingement cooling in the second cooling cavity 6, make the flow of cooling gas more even behind the vortex of second vortex post 9 again, carry out strong wave convection heat transfer to the wall simultaneously, at last cooling gas flows out in the air film hole 7 from the second cooling cavity 6, carry out air film cooling to the back of the leaf from air film hole 7 outflow at last.
Because the cooling gas just can follow air film hole 7 and flow out after first cooling chamber 5 and second cooling chamber 6, the heat transfer area of cold gas side increases by a wide margin, make air conditioning more abundant heat absorption along the journey, simultaneously through twice impact heat transfer, the comprehensive action has reduced the wall temperature level of blade down by a wide margin, the cooling effect of blade has been improved, can effectively solve the high-efficient problem of ablating of back of the leaf position, the air conditioning utilization ratio of blade has been promoted simultaneously, the temperature gradient of blade inside and outside wall has been reduced.
Preferably, the first cooling chamber 5 comprises a first impingement zone 10, a first turbulence zone 11 and a first convection zone 12, the first impingement zone 10 being arranged in correspondence with the first impingement hole 2, the first turbulence zone 11 being arranged around the first turbulence column 8, the first convection zone 12 being arranged in correspondence with the second impingement hole 4. A first turbulence area 11 is arranged between any adjacent first impact areas 10 in the first cooling chamber 5, and is specifically arranged as a first impact area 10-a first turbulence area 11-a first convection area 12-a first turbulence area 11-a first impact area 10; that is, after the first impact area 10 is subjected to impact cooling, the cooling air respectively flows to the first turbulent flow areas 11 at two sides, and reversely flows with the cooling air flowing out of the adjacent first turbulent flow areas 11, so that the heat convection is performed at the first convection area 12 between the two groups of first turbulent flow areas 11, and the high-efficiency cooling is realized.
Preferably, the second cooling chamber 6 comprises a second impact area 13, a second turbulence area 14 and a second convection area 15, the second impact area 13 is arranged corresponding to the second impact holes 4, the second turbulence area 14 is arranged around the second turbulence column 9, and the second convection area 15 is arranged corresponding to the film holes 7; the first impingement holes 2 and the second impingement areas 13 are staggered, and the first convection areas 12 and the second convection areas 15 are staggered. A second turbulence area 14 is arranged between any adjacent second impact areas 13 in the second cooling chamber 6, and is specifically arranged as a second impact area 13-a second turbulence area 14-a second convection area 15-a second turbulence area 14-a second impact area 13; that is, after the second impact area 13 is subjected to impact cooling, the cooling air respectively flows to the second turbulent flow areas 14 at two sides and reversely flows with the cooling air flowing out of the adjacent second turbulent flow areas 14, so that the heat convection is performed at the second convection area 15 between the two groups of second turbulent flow areas 14, and the efficient cooling is realized.
Preferably, the first turbulence columns 8 and the second turbulence columns 9 are arranged in a radially staggered manner, and the first turbulence columns 8 and the second turbulence columns 9 are at different height positions as seen in fig. 4, and since the inner layer wall 1, the middle layer wall 3 and the outer layer wall 16 are connected and supported through the first turbulence columns 8 and the second turbulence columns 9, the strength and stability of the support are effectively ensured by arranging the first turbulence columns 8 and the second turbulence columns 9 in a radially staggered manner.
Preferably, the first impingement openings 2 are arranged in correspondence with the film openings 7. Because the cooling gas continuously carries out convective heat transfer along with the flowing of the cooling gas in the flowing process of the cooling gas in the blade back, the temperature can be gradually increased, and the cooling effect is reduced; through corresponding the setting with first impact hole 2 and film hole 7, cooling gas can reverse flow after second impact hole 4, form U-shaped cooling flow path, the cooling hole region that the heat absorption is the most corresponds the minimum first impact hole 2 region of heat absorption, the better region of cooling effect in first cooling chamber 5 like this, through the backward flow back, it is relatively poor to locate the cooling effect at second cooling chamber 6, the region that cooling effect is relatively poor in first cooling chamber 5, through the backward flow back, it is better to cool off the effect in second cooling chamber 6, thereby the inside holistic even cooling of back of the leaf has been realized.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. The utility model provides a local high-efficient cooling structure of turbine blade back which characterized in that: comprises an inner layer wall (1), a middle layer wall (3) and an outer layer wall (16); the inner layer wall (1) is provided with a first impact hole (2), the middle layer wall (3) is provided with a second impact hole (4), the outer layer wall (16) is provided with an air film hole (7), a first cooling chamber (5) is formed between the inner layer wall (1) and the middle layer wall (3), and a second cooling chamber (6) is formed between the middle layer wall (3) and the outer layer wall (16); the first impact hole (2) and the second impact hole (4) are positioned at different positions of the blade in the radial direction, and the second impact hole (4) and the air film hole (7) are positioned at different positions of the blade in the radial direction; a first flow disturbing column (8) is connected between the inner layer wall (1) and the middle layer wall (3), and a second flow disturbing column (9) is connected between the middle layer wall (3) and the outer layer wall (16); the first turbulence column (8) and the first impact hole (2) as well as the second turbulence column (9) and the second impact hole are respectively positioned at different radial positions of the blade.
2. The turbine blade back local high efficiency cooling structure of claim 1, wherein: the first cooling chamber (5) comprises a first impact area (10), a first turbulent flow area (11) and a first convection area (12), the first impact area (10) is arranged corresponding to the first impact hole (2), the first turbulent flow area (11) is arranged around the first turbulent flow column (8), and the first convection area (12) is arranged corresponding to the second impact hole (4).
3. The turbine blade back local high efficiency cooling structure of claim 2, wherein: the second cooling chamber (6) comprises a second impact area (13), a second turbulent flow area (14) and a second convection area (15), the second impact area (13) is arranged corresponding to the second impact hole (4), the second turbulent flow area (14) is arranged around the second turbulent flow column (9), and the second convection area (15) is arranged corresponding to the air film hole (7); the first impact holes (2) and the second impact areas (13) are arranged in a staggered mode, and the first convection areas (12) and the second convection areas (15) are arranged in a staggered mode.
4. The turbine blade back local high efficiency cooling structure of claim 1, wherein: the first turbulence columns (8) and the second turbulence columns (9) are arranged in a radial staggered mode.
5. The turbine blade back local high efficiency cooling structure of claim 1, wherein: the first impact hole (2) and the air film hole (7) are arranged correspondingly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210369115.2A CN114718657B (en) | 2022-04-08 | 2022-04-08 | Turbine blade back local high-efficiency cooling structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210369115.2A CN114718657B (en) | 2022-04-08 | 2022-04-08 | Turbine blade back local high-efficiency cooling structure |
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| Publication Number | Publication Date |
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| CN114718657A true CN114718657A (en) | 2022-07-08 |
| CN114718657B CN114718657B (en) | 2024-06-11 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202210369115.2A Active CN114718657B (en) | 2022-04-08 | 2022-04-08 | Turbine blade back local high-efficiency cooling structure |
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Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3606572A (en) * | 1969-08-25 | 1971-09-20 | Gen Motors Corp | Airfoil with porous leading edge |
| US20090162209A1 (en) * | 2007-12-19 | 2009-06-25 | David John Wortman | Turbine engine components with environmental protection for interior passages |
| US8608430B1 (en) * | 2011-06-27 | 2013-12-17 | Florida Turbine Technologies, Inc. | Turbine vane with near wall multiple impingement cooling |
| CN204357500U (en) * | 2014-12-15 | 2015-05-27 | 中国燃气涡轮研究院 | A kind of turborotor embedded flow-disturbing pillar narrow channel cooling structure |
| CN107035417A (en) * | 2015-12-21 | 2017-08-11 | 通用电气公司 | Cooling circuit for many wall blades |
| US20190309634A1 (en) * | 2018-04-09 | 2019-10-10 | General Electric Company | Turbine airfoil multilayer exterior wall |
| CN111075510A (en) * | 2020-01-06 | 2020-04-28 | 大连理工大学 | Turbine blade honeycomb spiral cavity cooling structure |
| CN113090335A (en) * | 2021-05-14 | 2021-07-09 | 中国航发湖南动力机械研究所 | Impact air-entraining film double-wall cooling structure for turbine rotor blade |
-
2022
- 2022-04-08 CN CN202210369115.2A patent/CN114718657B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3606572A (en) * | 1969-08-25 | 1971-09-20 | Gen Motors Corp | Airfoil with porous leading edge |
| US20090162209A1 (en) * | 2007-12-19 | 2009-06-25 | David John Wortman | Turbine engine components with environmental protection for interior passages |
| US8608430B1 (en) * | 2011-06-27 | 2013-12-17 | Florida Turbine Technologies, Inc. | Turbine vane with near wall multiple impingement cooling |
| CN204357500U (en) * | 2014-12-15 | 2015-05-27 | 中国燃气涡轮研究院 | A kind of turborotor embedded flow-disturbing pillar narrow channel cooling structure |
| CN107035417A (en) * | 2015-12-21 | 2017-08-11 | 通用电气公司 | Cooling circuit for many wall blades |
| US20190309634A1 (en) * | 2018-04-09 | 2019-10-10 | General Electric Company | Turbine airfoil multilayer exterior wall |
| CN110359965A (en) * | 2018-04-09 | 2019-10-22 | 通用电气公司 | Turbine airfoil multilayer outer wall |
| CN111075510A (en) * | 2020-01-06 | 2020-04-28 | 大连理工大学 | Turbine blade honeycomb spiral cavity cooling structure |
| CN113090335A (en) * | 2021-05-14 | 2021-07-09 | 中国航发湖南动力机械研究所 | Impact air-entraining film double-wall cooling structure for turbine rotor blade |
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| CN114718657B (en) | 2024-06-11 |
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